Component for a turbine engine with a film hole

Abstract

An apparatus and method relating to a film hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.

What is claimed is: 
     
       1. A method of making a film hole of a predetermined inner dimension in a component of a turbine engine that generates a hot combustion gas flow, and provides a cooling fluid flow, where a wall separates the hot combustion gas flow from the cooling fluid flow and defines a hot surface along which the hot combustion gas flows in a hot flow path and a cooled surface facing the cooling fluid flow, the method comprising:
 forming a hole in the component with the hole having a layup portion facing away from the hot surface and providing the hole with an inner dimension greater than the predetermined inner dimension; 
 applying a coating to the component such that the coating fills in the layup portion leaving the hole with a dimension equivalent to the predetermined inner dimension. 
 
     
     
       2. The method of  claim 1  wherein the layup portion is provided on a portion of the hole. 
     
     
       3. The method of  claim 1  wherein the predetermined inner dimension defines a circle. 
     
     
       4. The method of  claim 3  wherein the layup portion comprises a crescent portion adjacent the circle. 
     
     
       5. The method of  claim 3  wherein the layup portion comprises a circle having a larger diameter than the predetermined inner dimension. 
     
     
       6. The method of  claim 1  wherein the hole comprises a conical section and the layup portion extends along the conical section. 
     
     
       7. The method of  claim 6  wherein the hole comprises a metering section upstream of the conical section. 
     
     
       8. The method of  claim 7  wherein the metering section comprises a circular cross section. 
     
     
       9. The method of  claim 1  wherein the coating comprises a substrate, bond coat, and one or more ceramic-based topcoats. 
     
     
       10. The method of  claim 1  wherein the film hole is made by machining via electro-discharge machining, 3-D printing, machining via a laser, or by casting in. 
     
     
       11. The method of  claim 1  wherein the inner dimension is at least one of a diameter, major axis or minor axis. 
     
     
       12. The method of  claim 1  wherein the hole has at least one of a circular or non-circular cross section. 
     
     
       13. An engine component for a turbine engine, which generates a hot combustion gas flow, and provides a cooling fluid flow, comprising:
 a wall separating the hot combustion gas flow from the cooling fluid flow and having a hot surface along which the hot combustion gas flows in a hot flow path and a cooled surface facing the cooling fluid flow; 
 at least one film hole comprising a predetermined inner dimension portion extending between a layup portion close to the hot surface and a laydown portion opposite the layup portion and close to the cooled surface, the layup portion located adjacent the predetermined inner dimension portion; and 
 a coating filling the layup portion. 
 
     
     
       14. The engine component of  claim 13  wherein the layup portion is provided on only a portion of the predetermined inner dimension portion. 
     
     
       15. The engine component of  claim 13  wherein the predetermined inner dimension portion is symmetrical about its centerline. 
     
     
       16. The engine component of  claim 15  wherein the predetermined inner dimension portion is a circle. 
     
     
       17. The engine component of  claim 15  wherein the layup portion and predetermined inner dimension portion collectively define an area asymmetrical to the centerline of the predetermined inner dimension portion. 
     
     
       18. The engine component of  claim 13  wherein the predetermined inner dimension portion is a circle. 
     
     
       19. The engine component of  claim 18  wherein the layup portion is a crescent. 
     
     
       20. The engine component of  claim 13  wherein the layup portion comprises a circle having a larger diameter than the predetermined inner dimension. 
     
     
       21. The engine component of  claim 13  wherein the film hole comprises a conical section and the layup portion extends along the conical section. 
     
     
       22. The engine component of  claim 21  wherein the film hole comprises a metering section upstream of the conical section. 
     
     
       23. The engine component of  claim 22  wherein the metering section comprises a circular cross section. 
     
     
       24. The engine component of  claim 23  wherein the coating comprises multiple layers.